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Energies 2020, 13, 1374 8 of 20 to a region of about one quarter of chord from the trailing edge. The streamline acceleration is quite evident too: they are deflected toward the airfoil. These modifications are expected to be beneficial for the local pressure and lift coefficients, CP and CL. Besides, since the wake of the airfoil is strongly reduced, a decrease of the drag coefficient can be expected too. O? = # N? > # N? $ # " ! 7I Figure 8. (a) Plasma-off and (b) plasma-on flow field at TA for α = 14.5◦ and U∞ = 20 m/s: The dashed line in panel a marks the position of the cross-wake velocity profiles presented in Figure 9. These effects are confirmed by the analysis of the cross-wake velocity profile and the estimation of CP, reported in the two following graphs. The former, Figure 9a, allows to compare two velocity profiles in the wake, corresponding to plasma-off and -on configurations. This and all the cross-wake velocity profiles are obtained retrieving the velocity values along an axis located at c/6 = 50 mm downstream of the trailing edge, evidenced in Figure 8a. Within the measurement domain, this location allows to determine mean values in a region less unsteady than the close proximity of the airfoil. As expected, in the upper and lower part of the domain, the velocity values are almost coincident with the freestream ones, while a momentum drop is visible in correspondence with the wake region. It can be noted, though, that, in the actuated case, represented by the red curve, the momentum drop is significantly reduced along with the region it interests. This contributes to the thinning of the wake and the reduction of its blockage. It should also be outlined that, in the upper part, the two curves do not coincide perfectly: the plasma-on case shows a lower velocity with respect to the plasma-off one. This may be explained considering that the actuator can affect the whole flow around the airfoil, modifying the circulation and the stagnation point position on the pressure side, which is indeed in the upper part of the figure. = > +FBB +F ,+F O? # # # ! " 7I N? Figure 9. (a) Cross-wake velocity profile and (b) CP values at TA for α = 14.5◦ and U∞ = 20 m/s. # +F ,+FPDF Image | Stall Control by Plasma Actuators: Characterization along the Airfoil Span
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